US10309244B2 - CMC shroud support system - Google Patents

CMC shroud support system Download PDF

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Publication number
US10309244B2
US10309244B2 US15/102,370 US201415102370A US10309244B2 US 10309244 B2 US10309244 B2 US 10309244B2 US 201415102370 A US201415102370 A US 201415102370A US 10309244 B2 US10309244 B2 US 10309244B2
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Prior art keywords
shroud
upper wall
hanger
segmented
cmc
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US20160312639A1 (en
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Jason David Shapiro
Roger Lee Doughty
Michael John Franks
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General Electric Co
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General Electric Co
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Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SHAPIRO, JASON DAVID, DOUGHTY, ROGER LEE, Franks, Michael John
Publication of US20160312639A1 publication Critical patent/US20160312639A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y02T50/672—

Definitions

  • the disclosed embodiments generally pertain to shrouds for a gas turbine engine. More particularly, but not by way of limitation, present embodiments relate to ceramic matrix composite (CMC) shroud support systems utilized in gas turbine engines including a clip structure for connecting the CMC shroud.
  • CMC ceramic matrix composite
  • a typical gas turbine engine generally possesses a forward end and an aft end with its several core or propulsion components positioned axially therebetween.
  • An air inlet or intake is located at a forward end of the engine. Moving toward the aft end, in order, the intake is followed by a compressor, a combustion chamber, and a turbine.
  • additional components may also be included in the engine, such as, for example, low-pressure and high-pressure compressors, and low-pressure and high-pressure turbines. This, however, is not an exhaustive list.
  • An engine also typically has an internal shaft axially disposed along a center longitudinal axis of the engine. The internal shaft is connected to both the turbine and the air compressor, such that the turbine provides a rotational input to the air compressor to drive the compressor blades.
  • air is pressurized in a compressor and mixed with fuel in a combustor for generating hot combustion gases which flow downstream through turbine stages. These turbine stages extract energy from the combustion gases.
  • a multi-stage high pressure turbine first receives the hot combustion gases from the combustor through a row of high pressure turbine rotor blades extending radially outwardly from a supporting rotor disk.
  • a low pressure turbine may be disposed downstream of the high pressure turbine for further conversion of gas energy to mechanical energy.
  • a shroud assembly circumscribes the turbine rotor and defines an outer boundary for combustion gases flowing through the turbine.
  • the turbine shroud may be a single unitary structure or may be formed of a plurality of segments.
  • Some known shroud assemblies include a shroud hanger that is coupled to an outer casing of the engine to provide support to a plurality of shrouds positioned adjacent to, and radially outward of, the tips of the turbine blades.
  • the shroud may move too far from adjacent blade tips allowing air leakage and decreasing efficiency.
  • a shroud and shroud hanger wherein at least the shroud is formed of ceramic matrix composite material.
  • the shroud and hanger extend in a circumferential direction.
  • a generally C-shaped clip extends radially to retain the hanger and shroud together.
  • a segmented shroud assembly comprises a shroud hanger which extends in a circumferential direction and has an axial dimension, a cavity disposed between an axial forward end and an axial rearward end and extending circumferentially, a ceramic matrix composite (CMC) shroud disposed within the cavity, the CMC shroud having a lower wall, at least one side wall, at least one upper wall and at least a partially hollow interior, a c-clip connecting the shroud hanger and the CMC shroud, the c-clip disposed at an end of the shroud hanger and engaging a lower surface of the upper wall.
  • CMC ceramic matrix composite
  • the clip may have an upper rib and a lower rib for engaging the shroud hanger and the CMC shroud.
  • the segmented shroud assembly may further comprise a baffle positioned within the at least partially hollow interior.
  • the segmented shroud assembly wherein the c-clip extends into a recess in the shroud hanger.
  • the recess may be formed to allow the c-clip to fit flush with a slash face of the shroud hanger.
  • the CMC shroud may have an opening in the upper wall. The opening may be centered between a first upper wall and a second upper wall.
  • the CMC shroud may further comprise a second opening at an end of the shroud.
  • the shroud may further comprise a support depending from one of the first upper wall and the second upper wall.
  • the segmented shroud assembly wherein one of the first and second upper wall are disposed at an end of the CMC shroud.
  • the segmented shroud assembly wherein the other of the first and second upper wall are disposed near an end of the CMC shroud.
  • the segmented shroud assembly wherein the support has a width in a circumferential dimension which is greater than a width of the one of the first upper wall and the second upper wall.
  • the segmented shroud assembly wherein the opening is disposed at a circumferential end of the upper wall.
  • the shroud may have a spacer disposed on the at least one upper wall.
  • FIG. 1 is a side section view of an exemplary embodiment of a gas turbine engine
  • FIG. 2 is an exploded assembly view of a C-clip supported shroud
  • FIG. 3 is an assembled view of the embodiment of FIG. 2 ;
  • FIG. 4 is an alternative embodiment of a C-clip supported shroud including a baffle
  • FIG. 5 is a first embodiment of a shroud for use with the C-clip support assembly
  • FIG. 6 is a second embodiment of a shroud for use with the C-clip support assembly
  • FIG. 7 is a third embodiment of a shroud for use with the C-clip support assembly
  • FIG. 8 is a fourth embodiment of a shroud for use with the C-clip support assembly.
  • FIG. 9 is a fifth embodiment of a shroud for use with the C-clip support assembly.
  • FIGS. 1-9 various embodiments of a C-clip supported Ceramic Matrix Composite (“CMC”) shroud support system is depicted.
  • the shroud and shroud hanger are connected by a C-clip to limit relative radial motion between the two components.
  • the shroud may have various forms in order to function with the shroud hanger.
  • the shroud hanger system may be utilized in various portions of the gas turbine engine including, but not limited to, high pressure and low pressure turbines as well as the compressor. All of these features improve any or all of manufacture, operation or performance.
  • axial refers to a dimension along a longitudinal axis of an engine.
  • forward used in conjunction with “axial” or “axially” refers to moving in a direction toward the engine inlet, or a component being relatively closer to the engine inlet as compared to another component.
  • aft used in conjunction with “axial” or “axially” refers to moving in a direction toward the engine nozzle, or a component being relatively closer to the engine nozzle as compared to another component.
  • the terms “radial” or “radially” refer to a dimension extending between a center longitudinal axis of the engine and an outer engine circumference.
  • proximal or “proximally,” either by themselves or in conjunction with the terms “radial” or “radially,” refers to moving in a direction toward the center longitudinal axis, or a component being relatively closer to the center longitudinal axis as compared to another component.
  • distal or disally, either by themselves or in conjunction with the terms “radial” or “radially,” refers to moving in a direction toward the outer engine circumference, or a component being relatively closer to the outer engine circumference as compared to another component.
  • lateral refers to a dimension that is perpendicular to both the axial and radial dimensions.
  • FIG. 1 a schematic side section view of a gas turbine engine 10 is shown.
  • the function of the turbine is to extract energy from high pressure and temperature combustion gases and convert the energy to mechanical energy for work.
  • the turbine 10 has an engine inlet end 12 wherein air enters the core or propulsor 13 which is defined generally by a multi-stage high pressure compressor 14 , a combustor 16 and a multi-stage high pressure turbine 20 . Collectively, the propulsor 13 provides thrust or power during operation.
  • the gas turbine 10 may be used for aviation, power generation, industrial, marine or the like.
  • the compressed air is mixed with fuel and burned providing the hot combustion gas which exits the combustor 16 and enters the high pressure turbine 20 .
  • energy is extracted from the hot combustion gas causing rotation of turbine blades which, in turn, cause rotation of the shaft 24 .
  • the shaft 24 passes toward the front of the engine to continue rotation of the one or more compressor stages 14 , a turbofan 18 or inlet fan blades, depending on the turbine design.
  • the turbofan 18 is connected by the shaft 28 to a low pressure turbine 21 and creates thrust for the turbine engine 10 .
  • the low pressure turbine 21 may also be utilized to extract further energy and power additional compressor stages.
  • the low pressure air may be used to aid in cooling components of the engine as well.
  • the assembly 30 includes a hanger 32 , a shroud 50 comprised of a plurality of shroud segments 51 and a retainer or c-clip 60 .
  • a baffle 80 ( FIG. 4 ) may optionally be used within the shroud segment 51 .
  • the baffle 80 may be disposed within the shroud 50 and may include apertures (not shown) to provide shroud cooling air from a known source through the baffle 80 to the shroud 50 .
  • the baffle may take various forms which fit within the shroud 50 and which provide backside impingement cooling to the shroud segment 51 .
  • a shroud hanger 32 which is connected to the engine casing and extends circumferentially about a portion of the engine, for example the turbine.
  • the engine casing extends circumferentially about the engine axis 26 ( FIG. 1 ).
  • Hangers 32 extend from the radially inward surface of the engine casing.
  • One or more hangers 32 may extend circumferentially about the engine casing corresponding to the circumferential shape of the turbine 20 .
  • the hangers 32 retain the one or more shroud segments 50 in circular configuration about the engine axis 26 ( FIG. 1 ) and the shroud segments 50 define the flow boundary within portions of the engine, for non-limiting example the compressor 14 or turbine 20 .
  • the shroud hanger 32 is defined by a plurality of segments which in combination, extend about the central axis 26 of the engine.
  • the shroud hanger 32 may include a first wall 34 a second wall 36 , each of which extend in a radial direction and in a circumferential direction.
  • the first wall 34 may be a one-piece linear structure and may extend in a substantially radial direction when mounted in the engine 10 .
  • the first wall 34 may be formed of a plurality of segments, linear, curvilinear or a combination of both.
  • the second wall 36 may also be linear or may be formed of segments.
  • the second wall 36 for example, may have two radially extending segments 31 and 33 and an axially extending 39 portion between the radially extending segments.
  • a hanger gusset 38 may extend between the first wall 34 and the second wall 36 and may extend axially or may extend at an angle to the central axis 26 as depicted. According to instant embodiment, the gusset 38 is tapered from a lower radial height 42 at the first wall 34 to a higher radial height 44 at the second wall 36 . The gusset 38 may alternatively be flat or tapered in the opposite direction.
  • the shroud hanger 32 includes tabs or hooks 35 , 37 which may be utilized to engage the engine casing.
  • the tabs 35 , 37 may extend continuously in a circumferential direction or may be defined by tabs at specific locations where connections occur to save weight.
  • These hooks 35 , 37 may take various forms in order to provide a mounting assembly or structure.
  • the depicted embodiment has a generally inverted L-shaped cross-section in combination with the first and second walls 34 , 36 .
  • the shroud 50 may be formed of one or more shroud segments 51 .
  • the lower most surface of the shroud segment 51 defines an outer surface of an air flow path within the gas turbine engine 10 , for example a compressor 14 or turbine 20 .
  • the segments 51 may further comprise an abradable material on the lowermost surface 58 .
  • Radially inward from the shroud segment 51 may be an airfoil blade 23 which rotates during operation of the gas turbine engine 10 with a rotor disk.
  • the assembly 30 includes a shroud hanger 32 and a side section view of exemplary shroud support system 30 is depicted.
  • the turbine 20 includes a row of circumferentially spaced stationary vanes (not shown) and a plurality of circumferentially spaced turbine blades (not shown) downstream of the vanes.
  • the blades are foil-shaped and mounted to a turbine rotor disk (not shown).
  • Each of the blades 23 extends radially toward a shroud 50 .
  • the shroud 50 extends circumferentially about the engine axis 26 and is comprised of a plurality of shroud segments 51 .
  • the shroud 50 may be formed of one unitary structure.
  • the shroud 50 is tightly configured relative to the blades 23 so that the shroud 50 defines an outer radial flowpath boundary for the hot combustion gas flowing through the turbine 20 .
  • a ceramic matrix composite (CMC) shroud 50 is positioned within the cavity 46 of the shroud hanger 32 .
  • the shroud 50 defines a structure which is disposed against the rotor blade tips of, for example, the turbine 20 .
  • the shroud 50 may be positioned within the cavity 46 and is sized and shaped to be positioned within the cavity 46 .
  • the shroud segments 50 include end faces 52 which are commonly referred to as “slash faces.”
  • the slash faces 52 , 54 may lie in plane parallel to the center line axis of the engine 10 , referred to as a “radial plane”, or they may be slightly offset from the radial plane, or otherwise oriented so that they are at an acute angle to such radial plane.
  • Each shroud 50 includes a top wall 56 , a bottom wall 58 and at least one side wall 59 .
  • the instant embodiment includes a second side wall or transition wall 57 opposite the first side wall 59 which extends substantially between the top wall 56 and the bottom wall 58 .
  • the shroud 50 may or may not include one or more windows or relief sections (not shown), which in combination with adjacent relief sections of adjacent segments 50 form apertures.
  • the windows may be fully bounded within the top surface of the shroud 50 .
  • the second window may also be fully bounded within the top surface of the shroud 50 or alternatively may be disposed at circumferential ends of the shroud 50 , at a slash face 52 , 54 , so that adjacent shrouds 50 form a complete window.
  • the shroud 50 has a plurality of circumferentially spaced apertures formed by adjacent relief windows located in the top wall 56 .
  • the shroud 50 may be supported from the hanger 32 at these locations or at ends of the shroud segment 51 .
  • end gaps may be positioned in the slash faces 52 , 54 and 48 , 49 . These gaps may be used to position one or more spline seals. These spline seals may be formed of thin strips of metal or other suitable materials which are inserted in slots or gaps at the end faces to span the gaps between adjacent segments and limit air leakage between the hangers 32 and the shrouds 50 .
  • the shroud segments 50 may be constructed of various low ductility and low coefficient of thermal expansion materials including but not limited to a ceramic matrix composite (CMC).
  • CMC materials include a ceramic fiber, for example a silicon carbide (SiC), forms of which are coated with a compliant material such as boron nitride (BN). The fibers are coated in a ceramic type matrix, one form of which is silicon carbide (SiC).
  • the shroud segment 40 can also be constructed of other low-ductility, high-temperature-capable materials.
  • CMC materials generally have room temperature tensile ductility of less than or equal to about 1% which is used herein to define a low tensile ductility material.
  • CMC materials have a room temperature tensile ductility in the range of about 0.4% to about 0.7%.
  • CMC materials have a characteristic wherein the materials tensile strength in the direction parallel to the length of the fibers (the “fiber direction”) is stronger than the tensile strength in the direction perpendicular.
  • This perpendicular direction may include matrix, interlaminar, secondary or tertiary fiber directions.
  • Various physical properties may also differ between the fiber and the matrix directions.
  • a C-clip 60 is positioned for use.
  • the clip includes a first leg 62 , a second leg 64 and third leg 66 extending between the first leg 62 and second leg 64 .
  • the first leg 62 of the C-clip 60 engages a recess 45 in the slash face 48 of the hanger 32 .
  • the second leg 64 of the C-clip 60 engages a lower surface of the upper wall 56 .
  • the C-clip 60 is forced in a circumferential direction so that the third leg 66 engages the slash faces 48 , 52 .
  • a similar construction is utilized on the opposite end of the shroud hanger 32 and the shroud 50 .
  • FIG. 3 an assembled view of the shroud assembly 30 is depicted.
  • the C-clip 60 is positioned within the recess 45 and beneath the upper wall 56 of the shroud 50 .
  • the C-clip 60 retains the shroud hanger 32 and the shroud 50 together in the radial direction and limits relative radial motion between the two parts.
  • the C-clip 60 may be utilized at ends of the shroud hanger 32 . However, due to the arrangements of the shroud segments 51 , the C-clips 60 may be engaging the segments at various locations including either of the slash faces 52 , 54 or through openings in the top wall 56 of the shroud 50 .
  • the C-clips 60 include the first leg 62 and the second leg 64 which extend in a generally tangential or circumferential direction.
  • the third leg 66 extends radially between the first and second legs 62 , 64 .
  • the C-clips 60 may be friction fit to engage the shroud hanger 32 and the shroud 50 .
  • the upper surface 56 of the shroud engages a cavity surface of the hanger 32 . Additionally, the transition surface 57 may be engages by edges or a surface of the hanger 32 for additional stability. Ends of the shroud 50 may also engage portions of the hanger 32 for added stability.
  • FIG. 4 a side section view of an alternate embodiment is depicted.
  • the C-clip 160 is shown engaging the shroud hanger 32 .
  • the side section view of the hanger 32 depicts the recess 45 and the C-clip 160 extending into the recess 45 .
  • the lower or second leg 165 extends in a circumferential direction to capture the shroud 50 and, optionally, a baffle 80 .
  • the baffle 80 may be utilized to direct cooling air to the interior of the shroud 50 .
  • the C-clip or retainer 160 may be flush with the slash faces of the shroud or hanger which allows for sealing between the segments.
  • the flush fit may be provided in a variety of manners and according to one exemplary embodiment, the recess 45 is defined by two recess walls 43 , 47 .
  • the lower wall 47 is shorter in length in the circumferential direction so that when positioned in the retaining position, the outer surface of the c-clip 160 is substantially flush with the slash face of the hanger 32 . This allows flush fit of adjacent hangers 32 in the circumferential direction.
  • the C-clips differ slightly.
  • the third leg 66 of the C-clip 60 is linear in nature and of a constant thickness.
  • the third leg 166 has tapered portions 167 causing the thickness of the third leg 166 to vary in thickness providing proper spacing of the C-clip 160 in the circumferential direction.
  • internal corners of the clip 160 may also have reliefs 168 to allow stress relief during flexing and thermal growth.
  • first and second legs 161 , 165 may include ribs or protrusions 163 of a different thickness so as to engage the hanger 32 , shroud 50 and optionally, baffle 80 with the appropriate fit and provide additional strength to the C-clips 60 , 160 .
  • the cross-sectional view of FIG. 4 also depicts spacing structures utilized with the shroud 50 and the baffle 80 .
  • the shroud 50 includes a spacing rib 53 extending in a radial direction to provide spacing between the hanger 32 and the shroud 50 .
  • the rib 51 may be continuous in the circumferential direction or may be discontinuous in the circumferential direction.
  • the baffle 80 may include a spacing rib 81 which extends radially from the baffle toward the shroud 50 .
  • the ribs 51 , 81 are depicted in some embodiments extending from upper surfaces of the shroud 50 and the baffle 80 . However, in alternate embodiments, the ribs may extend from alternate surfaces or may extend from the hanger 32 in order to provide proper spacing.
  • the shroud segment 151 is generally shaped similarly to the embodiment of FIGS. 2 and 3 . Additionally, the embodiment includes windows or relief areas 162 , 164 as previously described. These windows provide weight reduction for the shroud 150 .
  • the window 162 is completely enclosed in the top wall 156 .
  • the window 164 is partially disposed within the top wall 156 so that upon mating with an adjacent shroud segment 151 , the second window or relief 164 will be fully formed.
  • the shroud segment 151 may fully enclose two or more windows depending on the circumferential length of the segment.
  • the center support 170 may be oblong in cross-section according to one embodiment however, various cross-sectional shapes may be utilized.
  • the “center support” 170 provides additional strength for the support or top wall 156 in the center of the shroud segment 151 .
  • the center support 170 may also be used to hang the shroud 150 from a hanger, for example hanger 32 .
  • the term center is used because the embodiment depicted is a partial shroud segment 151 and the segment support 170 is located at the center of the embodiment of segment 151 .
  • the segment shows a window 164 partially formed, embodiments, may be provided wherein the segment is longer or shorter than depicted in this and other embodiments of this disclosure.
  • the shroud 150 may be formed of one or more shroud segments.
  • an isometric view of an alternate shroud 250 is a segment of a portion of a complete segment 251 .
  • the structure has a single window 262 rather than two windows in the top wall 256 of the segment.
  • the single window is depicted at an end of the segment 251 .
  • the segment 251 may be longer wherein the window 262 is centrally located or alternatively positioned and either fully enclosed or partially enclosed.
  • shroud 350 a further alternate embodiment of a shroud 350 is depicted.
  • the shroud top wall 356 is solid and therefore, does not have any of the weight reducing relief or windows of the previous embodiments.
  • the shroud segment 351 is hollow. While the shrouds are depicted as hollow, they may alternatively be partially hollow for improved strength or other desirable characteristics.
  • FIG. 8 a further embodiment is depicted of an alternate shroud 450 .
  • This embodiment includes top wall 456 only at ends of the shroud segment 451 . Again, this embodiment shows half of a single segment and accordingly, the window or relief 462 extends almost the entire circumferential distance of the top wall 456 .
  • FIG. 9 depicts a further alternative wherein the shroud 550 is shown in part.
  • the structure includes two windows 562 , 564 for weight relief and a support 556 extending there between and defining part of the top wall of the shroud 550 .
  • the structure does not include a center support as with the embodiment of FIG. 5 .
  • inventive embodiments are presented by way of example only and that, within the scope of the appended claims and equivalents thereto, inventive embodiments may be practiced otherwise than as specifically described and claimed.
  • inventive embodiments of the present disclosure are directed to each individual feature, system, article, material, kit, and/or method described herein.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Ceramic Products (AREA)
US15/102,370 2013-12-12 2014-12-04 CMC shroud support system Active 2035-10-31 US10309244B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US15/102,370 US10309244B2 (en) 2013-12-12 2014-12-04 CMC shroud support system

Applications Claiming Priority (3)

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CA2932612A1 (fr) 2015-06-18
US20160312639A1 (en) 2016-10-27
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